US7160078B2 - Mechanical solution for rail retention of turbine nozzles - Google Patents

Mechanical solution for rail retention of turbine nozzles Download PDF

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Publication number
US7160078B2
US7160078B2 US10/947,450 US94745004A US7160078B2 US 7160078 B2 US7160078 B2 US 7160078B2 US 94745004 A US94745004 A US 94745004A US 7160078 B2 US7160078 B2 US 7160078B2
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United States
Prior art keywords
nozzle
turbine
segment
rail
support ring
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US10/947,450
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English (en)
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US20060062673A1 (en
Inventor
Robert Walter Coign
David John Humanchuk
Leslie Tucker
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General Electric Co
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General Electric Co
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Publication date
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Priority to US10/947,450 priority Critical patent/US7160078B2/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: TUCKER, LESLIE R., COIGN, ROBERT WALTER, HUMANCHUK, DAVID JOHN
Priority to JP2005273095A priority patent/JP4778758B2/ja
Priority to DE102005045459.3A priority patent/DE102005045459B4/de
Priority to CN200510106321.0A priority patent/CN1752416B/zh
Publication of US20060062673A1 publication Critical patent/US20060062673A1/en
Application granted granted Critical
Publication of US7160078B2 publication Critical patent/US7160078B2/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • the present invention relates to gas turbines, and in particular, to a mechanical arrangement for the rail retention of turbine nozzles that protects against catastrophic nozzle failures.
  • a typical practice includes stage 1 nozzles positively attached at the outer retaining ring only, which provides axial, radial, and circumferential restraints. At the inner rail of the nozzle, only axial restraint is provided through contact at the nozzle chordal land seal. This chordal land seal concept allows the large transient radial growth differentials, while allowing the nozzle to rotate about the outer retaining ring hook due to axial growth differentials between the inner and outer turbine cases.
  • the present invention relates to a mechanical arrangement for an inner-rail retention of a singlet nozzle that protects against catastrophic nozzle failures, although it should be noted that the present invention can also be used with doublet or triplet nozzle designs.
  • a mechanical arrangement for the inner rail retention of a singlet nozzle to provide protection against catastrophic nozzle failures which includes a turbine nozzle segment having at least one stator vane and including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with said rail on one side thereof, an inner retainer segment secured to said inner support ring and in part in axially spaced registration relative to said rail on an axial side of said rail opposite from said support ring, a first inclined conical surface on the inner retainer segment, and a second inclined conical surface on the inner platform rail of the turbine nozzle, the second inclined conical surface opposing the first inclined conical surface, whereby the two opposing inclined conical surfaces bind the inner platform rail to the turbine nozzle between the inner retainer segment and the inner support ring resulting in a wedge lock that prevents the inner platform of nozzle from being lost downstream into rotating hardware of the turbine.
  • the present invention also encompasses a method of preventing a catastrophic nozzle failure in a turbine having a plurality of nozzle segments arranged about a turbine axis with each segment having at least one stator airfoil and an inner platform carrying an inner platform rail and inner nozzle support rings in part in spaced axial registration with said rails, the method including the steps of providing a plurality of inner retainer segments secured to said inner supporting rings and in part in axial spaced registration relative to said rails on an axial side of said rails opposite from said support rings, providing a plurality of first inclined conical surfaces on each of the inner retainer segments, and providing a plurality of second inclined conical surfaces on each of the inner platform rails, each second inclined conical surface opposing a corresponding first inclined conical surface, whereby, in response to a structural failure in the turbine nozzle segment, the two opposing inclined conical surfaces contact and bind a corresponding inner platform rail to a corresponding nozzle segment between a corresponding inner retainer segment and a corresponding inner support ring
  • FIG. 1 is a schematic cross-sectional view showing the positional relationship of the inner retainer to the surrounding hardware of a 6C turbine, and in particular, the first stage of such a turbine.
  • FIG. 2 is a schematic frontal view (upper half only) of the inner retainer as applied to a 6C turbine, which shows the inner support ring flanges that require multiple segments around the diameter.
  • FIG. 3 is a more detailed schematic cross-sectional view of the inner retainer mechanical arrangement of the present invention showing the positional relationship of the inner retainer to the surrounding turbine hardware, including the stage 1 nozzle, inner support ring, spacer, and seal, as applied in the 6C type of turbine.
  • FIG. 4 shows the arrangement of FIG. 3 in a post failure situation, where the liberated nozzle inner platform/rail is wedged between the inner retainer and the inner support ring.
  • the present invention is directed to a mechanical arrangement for the inner rail retention of a singlet nozzle to provide protection against catastrophic nozzle failures, although it should be noted that the present invention can also be used with doublet or triplet nozzle designs.
  • the inner retention design of the present invention solves the lack of inner restraint while maintaining a flexible boundary that allows differential growth/movement between the inner and outer cases of a turbine.
  • the present invention balances the need for ease of installation and removal, with no increase in cooling flow leakage, and provides a focus on domestic object damage (“DOD”) resistance.
  • DOD domestic object damage
  • the inner retainer of the present invention provides positive retention against complete downstream loss of the inner portion of the failed nozzle to protect against catastrophic nozzle failure. Retention is accomplished by the fact that the inner rail of the nozzle must move radially outboard and then aft into the turbine flowstream. Through the use of opposing incline surfaces, one on the retainer and the other on the nozzle inner rail, a wedge lock is accomplished which holds the inner nozzle in place. Thus, even if the inner nozzle platform rotates backward and potentially causes a rub on the stage 1 bucket platform leading edge, the failure mode is much less severe than a complete loss of large pieces of hardware.
  • FIG. 1 illustrated in FIG. 1 is a cross-sectional view of a first stage turbine section 10 of a 6C turbine (not shown), which includes a first stage nozzle 12 and a first stage bucket 14 forming part of a rotor 16 .
  • FIG. 2 illustrates a front view of first stage nozzle 12 's segments.
  • Nozzle 12 is formed from a plurality of nozzle segments 13 , including an outer band or platform 18 , an inner band or platform 20 , and one or more airfoils 22 extending between platforms 18 and 20 .
  • the nozzle airfoils 22 extend in the hot gas path of the turbine, the hot gas path having a flow direction designated by the arrow 24 in FIG.
  • Airfoils 22 and buckets 14 are arranged in annular arrays about an axis of the turbine. Outer platform 18 of each nozzle segment 13 is secured to an outer retaining ring 26 .
  • Each of the nozzle segments includes a radially inwardly directed inner platform rail 28 , the aft face of which bears against an inner support ring 30 precluding axial movement in an aft direction.
  • the aft face of each rail 28 has an arcuate projecting land 31 for sealing against the forward axial face of the inner support ring 30 , the rails 28 forming an annular chordal seal about the upper and lower halves of the support ring 30 .
  • Each of the chordal land seals 32 typically comprises a narrow raised arcuate land 31 integral to the face of the rail 28 forming with adjacent nozzles a complete circumferential array of chordal land seals 32 bearing against the support rings 30 .
  • each of the arcuate inner retainer spacers 38 can be part of the support ring 30 , or alternatively, part of the retainer segment 36 .
  • the radial outer margins 40 of the inner retainer segments 36 are axially enlarged in a direction toward the inner support ring 30 , but are spaced from the rails 28 extending between the retainer segments 36 and support ring 30 .
  • the radial inner margins of the inner platform rails 28 are axially enlarged in a direction away from the inner support ring 30 .
  • nozzle segments 13 there are thirty-two nozzle segments 13 forming an annular array of nozzle airfoils 22 about the turbine axis and preferably six each of the inner retainer segments 36 and inner retainer spacers 38 , each of the segments 36 and the spacers 38 being disposed in an annular array about the axis of the turbine.
  • the region 42 forward of the inner retainer segments 36 receives cooling air, i.e., compressor discharge air under high pressure, and it is essential to seal the high pressure region 42 from the lower pressure region 44 adjacent to the forward rotor rim cavity and also the hot gas path outboard of the rim cavity.
  • first stage nozzle 12 is supported at outer platform 18 by an outer rail hook 17 to an aft hook 19 of outer retaining ring 26 .
  • Inner platform 20 is supported at chordal land seal 32 of an inner platform rail 28 by contact with inner support ring 30 .
  • An inner retainer 36 is comprised of a plurality of segments, and is bolted and pinned through a plurality of seals 39 and spacers 38 to inner support ring 30 .
  • FIG. 2 a portion of the first stage nozzle segments are shown in positional relation to outer retaining ring 26 and inner support ring 30 .
  • outer retaining ring 26 and inner support ring 30 For clarity, only the upper half of such nozzle segments are shown in FIG. 2 , but may be extended 180° about the engine center line for a complete graphical representation of such nozzle segments.
  • Multiple support ring flanges/ribs 23 which require multiple inner retaining segments 37 , can be seen in FIG. 2 .
  • Inner retainer ring 36 consists of six separate plate segments 37 whose arc lengths are sized to accommodate raised structural flanges/ribs 23 on inner support ring 30 . Although complicating the design, the segmentation of retainer 36 allows for ease of installation, even with a turbine's outer shell installed. After installation of nozzle 12 , each inner retainer 36 is installed from the front and then bolted through a seal 39 and a spacer 38 to inner support ring 30 . Close tolerance dowel pins 34 ( FIG. 1 ) are used to carry a failed nozzle 12 load via shear through the support ring 30 .
  • a typical failure mode would be a crack 25 in airfoil 22 of nozzle 12 that propagates completely through airfoil 22 .
  • Crack 25 as shown in FIG. 1 , is only illustrative, and could occur anywhere along the span of nozzle 12 . If such a crack 25 were to occur, nozzle 12 would separate into two pieces, i.e., outer platform 18 and inner platform 20 , respectively, each containing a particular segment of nozzle 12 's airfoil 22 . With such a separation in a prior turbine design, inner platform 20 would become loose hardware without the addition of inner retainer ring 36 to provide restraint at inner rail 28 .
  • inner retainer ring 36 a more detailed schematic cross-sectional view of inner retainer ring 36 is provided, showing the positional relationship of inner retainer 36 to the surrounding hardware, including the stage 1 nozzle inner rail 28 , inner support ring 30 , and spacer 38 and seal 39 , as applied in a 6C turbine.
  • inner retainer ring 36 is mounted in close proximity to nozzle inner rail 28 , there is no direct contact between the two parts.
  • the gaps between inner retainer ring 36 and nozzle inner rail 28 are optimized to be at a minimum, yet allow nozzle 12 to move through its complete range of transient motion.
  • the retention function is performed by two opposing inclined conical surfaces, i.e., one surface 50 on the inner retainer 36 and one surface 52 on the inner rail 28 of nozzle 12 . Also, with no physical contact, the inner retainer 36 provides no impact on cooling air leakage across the nozzle chordal land seal 32 .
  • FIG. 4 shows a post failure situation for the arrangement shown in FIG. 3 wherein the liberated nozzle inner rail 28 is wedged between inner retainer 36 and inner support ring 30 .
  • the inner retainer seal 39 has been removed from the view shown in FIG. 4 for clarity purposes.
  • a failure such as crack 25 in vane 22 of nozzle 12
  • the remaining balance of inner platform 20 (see FIG. 1 ) of nozzle 12 would have to move radially outboard away from the engine centerline and then downstream, as shown by arrow 54 in FIG. 4 .
  • the two opposing inclined surfaces, 50 and 52 contact and bind the inner rail 28 between the inner retainer 36 and inner support ring 30 .
  • the resulting wedge lock shown in the dashed circle in FIG. 4 prevents inner platform 20 of nozzle 12 from being lost downstream into rotating hardware, such as the stage 1 bucket 36 , to thereby protect against catastrophic nozzle failure.
  • the present invention also encompasses a method of preventing a catastrophic nozzle failure in a turbine having a plurality of nozzle segments 13 arranged about a turbine axis with each segment 13 having at least one stator airfoil 22 and an inner platform 20 carrying an inner platform rail 28 and inner nozzle support rings 30 in part in spaced axial registration with the rails 28 .
  • the method includes the steps of providing a plurality of inner retainer segments 36 secured to the inner supporting rings 30 and in part in axial spaced registration relative to the rails 28 on an axial side of the rails opposite from the support rings 30 , providing a plurality of first inclined conical surfaces 50 on each of the inner retainer segments 36 , and providing a plurality of second inclined conical surfaces 52 on each of the inner platform rails 28 , each second inclined conical surface 52 opposing a corresponding first inclined conical surface 50 , such that in response to a structural failure in the turbine nozzle segment 13 , the two opposing inclined conical surfaces contact and bind a corresponding inner platform rail 28 to a corresponding nozzle segment 13 between a corresponding inner retainer segment 36 and a corresponding inner support ring 30 .
  • the inner rail retention mechanical arrangement of the present invention has particular application with singlet nozzles in providing protection against catastrophic nozzle failures, as noted above, the present invention can also be used with doublet or triplet nozzle designs.
  • the inner rail retention mechanical arrangement of the present invention has been described with reference to a 6C type of turbine, it can be used with other types of turbines. Modifications to for other engine applications could include 1) a different number and length of retainer segments (as opposed to the 6 at approximately 60 degrees matched to the 6C turbine), since more or less may be desirable in other engines, 2) scaling up or down of parts to match a given engine size, 3) eliminating spacer 38 so that it becomes part of support ring 30 , or combining it into retainer plate 36 as one piece, 4) changing the angle or shape of inclined surfaces 50 and 52 , and 5) if nozzle 12 is inverted or attached at an outer platform rail instead of inner platform rail 28 , as in the 6C turbine, retainer 36 could be used at the outer rail.
  • the outer rail would bear against an outer support ring, and there would be a plurality of arcuate outer retainer segments like retainer 36 spaced from the outer support rail by a plurality of arcuate outer retainer spacers.
  • the radial inner margins of the outer retainer segments would also be axially enlarged in a direction toward the outer support ring and the radial outer margins of the outer platform rail is axially enlarged in a direction away from the outer support ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US10/947,450 2004-09-23 2004-09-23 Mechanical solution for rail retention of turbine nozzles Active 2024-11-26 US7160078B2 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US10/947,450 US7160078B2 (en) 2004-09-23 2004-09-23 Mechanical solution for rail retention of turbine nozzles
JP2005273095A JP4778758B2 (ja) 2004-09-23 2005-09-21 タービンノズルのレール保持のための機械的解決法
DE102005045459.3A DE102005045459B4 (de) 2004-09-23 2005-09-22 Mechanische Lösung zur Schienenhalterung von Turbinendüsen
CN200510106321.0A CN1752416B (zh) 2004-09-23 2005-09-23 涡轮喷嘴的杆保持结构

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Application Number Priority Date Filing Date Title
US10/947,450 US7160078B2 (en) 2004-09-23 2004-09-23 Mechanical solution for rail retention of turbine nozzles

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US7160078B2 true US7160078B2 (en) 2007-01-09

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JP (1) JP4778758B2 (de)
CN (1) CN1752416B (de)
DE (1) DE102005045459B4 (de)

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* Cited by examiner, † Cited by third party
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US20130108434A1 (en) * 2011-10-26 2013-05-02 Snecma Method for mounting a stator blading of a turbomachine, an engine casing and a turbomachine comprising at least one stator blading mounted on this engine casing
US8684683B2 (en) 2010-11-30 2014-04-01 General Electric Company Gas turbine nozzle attachment scheme and removal/installation method
US9528392B2 (en) 2013-05-10 2016-12-27 General Electric Company System for supporting a turbine nozzle
US20160377087A1 (en) * 2015-06-24 2016-12-29 MTU Aero Engines AG Seal carrier, guide vane ring and turbomachine
US20170096899A1 (en) * 2015-10-02 2017-04-06 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine disk
US20180058262A1 (en) * 2016-08-23 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine and method of attaching a turbine nozzle guide vane segment of a gas turbine
US20190153883A1 (en) * 2017-11-21 2019-05-23 Doosan Heavy Industries & Construction Co., Ltd. First-stage turbine vane supporting structure and gas turbine including same
US10539030B2 (en) 2013-02-26 2020-01-21 United Technologies Corporation Gas turbine engine stator vane platform reinforcement

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US20080050222A1 (en) * 2006-08-23 2008-02-28 General Electric Company Singlet welded nozzle hybrid design for a turbine
GB0619426D0 (en) * 2006-10-03 2006-11-08 Rolls Royce Plc A vane arrangement
US7824152B2 (en) * 2007-05-09 2010-11-02 Siemens Energy, Inc. Multivane segment mounting arrangement for a gas turbine
JP5134505B2 (ja) * 2008-11-07 2013-01-30 三菱重工業株式会社 排気タービン過給機のノズル取付構造
US9039350B2 (en) 2012-01-09 2015-05-26 General Electric Company Impingement cooling system for use with contoured surfaces
US9011079B2 (en) 2012-01-09 2015-04-21 General Electric Company Turbine nozzle compartmentalized cooling system
US9011078B2 (en) 2012-01-09 2015-04-21 General Electric Company Turbine vane seal carrier with slots for cooling and assembly
US9133724B2 (en) 2012-01-09 2015-09-15 General Electric Company Turbomachine component including a cover plate
US8944751B2 (en) 2012-01-09 2015-02-03 General Electric Company Turbine nozzle cooling assembly
US8864445B2 (en) 2012-01-09 2014-10-21 General Electric Company Turbine nozzle assembly methods
JP5675674B2 (ja) * 2012-02-29 2015-02-25 三菱重工業株式会社 タービン動翼の抜け止め構造およびこれを備えた回転機械
CN102733868B (zh) * 2012-07-06 2015-12-09 中国航空动力机械研究所 动力机械
EP2696039B1 (de) * 2012-08-10 2015-07-29 MTU Aero Engines GmbH Gasturbinenstufe
JP6363232B2 (ja) * 2014-06-12 2018-07-25 ゼネラル・エレクトリック・カンパニイ シュラウドハンガーアセンブリ
JP6314049B2 (ja) * 2014-07-24 2018-04-18 三菱日立パワーシステムズ株式会社 回転機械の静止部材及びガスタービン
DE102016202519A1 (de) * 2016-02-18 2017-08-24 MTU Aero Engines AG Leitschaufelsegment für eine Strömungsmaschine
US11428241B2 (en) 2016-04-22 2022-08-30 Raytheon Technologies Corporation System for an improved stator assembly
US20180328228A1 (en) * 2017-05-12 2018-11-15 United Technologies Corporation Turbine vane with inner circumferential anti-rotation features
US10968777B2 (en) * 2019-04-24 2021-04-06 Raytheon Technologies Corporation Chordal seal
IT201900014739A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
DE102020115106B4 (de) * 2020-06-08 2022-08-25 Man Energy Solutions Se Turbinenleitapparat

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4720236A (en) * 1984-12-21 1988-01-19 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US5839878A (en) * 1996-09-30 1998-11-24 United Technologies Corporation Gas turbine stator vane
US6609885B2 (en) * 2001-12-28 2003-08-26 General Electric Company Supplemental seal for the chordal hinge seal in a gas turbine
US20050111969A1 (en) * 2003-11-20 2005-05-26 General Electric Company Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction
US20050244267A1 (en) * 2004-04-29 2005-11-03 General Electric Company System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1387866A (en) * 1972-06-21 1975-03-19 Rolls Royce Aerofoil members for gas turbine engines
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
US5224822A (en) * 1991-05-13 1993-07-06 General Electric Company Integral turbine nozzle support and discourager seal
CA2070511C (en) * 1991-07-22 2001-08-21 Steven Milo Toborg Turbine nozzle support
DE10340825A1 (de) * 2003-09-04 2005-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Laufspaltkontrolle

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4720236A (en) * 1984-12-21 1988-01-19 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US5839878A (en) * 1996-09-30 1998-11-24 United Technologies Corporation Gas turbine stator vane
US6609885B2 (en) * 2001-12-28 2003-08-26 General Electric Company Supplemental seal for the chordal hinge seal in a gas turbine
US20050111969A1 (en) * 2003-11-20 2005-05-26 General Electric Company Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction
US20050244267A1 (en) * 2004-04-29 2005-11-03 General Electric Company System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8684683B2 (en) 2010-11-30 2014-04-01 General Electric Company Gas turbine nozzle attachment scheme and removal/installation method
US9366150B2 (en) * 2011-10-26 2016-06-14 Snecma Method for mounting a stator blading of a turbomachine, an engine casing and a turbomachine comprising at least one stator blading mounted on this engine casing
US20130108434A1 (en) * 2011-10-26 2013-05-02 Snecma Method for mounting a stator blading of a turbomachine, an engine casing and a turbomachine comprising at least one stator blading mounted on this engine casing
US10539030B2 (en) 2013-02-26 2020-01-21 United Technologies Corporation Gas turbine engine stator vane platform reinforcement
US9528392B2 (en) 2013-05-10 2016-12-27 General Electric Company System for supporting a turbine nozzle
US10533569B2 (en) * 2015-06-24 2020-01-14 MTU Aero Engines AG Seal carrier, guide vane ring and turbomachine
US20160377087A1 (en) * 2015-06-24 2016-12-29 MTU Aero Engines AG Seal carrier, guide vane ring and turbomachine
US20170096899A1 (en) * 2015-10-02 2017-04-06 Doosan Heavy Industries & Construction Co., Ltd. Gas turbine disk
US10605085B2 (en) * 2015-10-02 2020-03-31 DOOSAN Heavy Industries Construction Co., LTD Gas turbine disk
US20180058262A1 (en) * 2016-08-23 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine and method of attaching a turbine nozzle guide vane segment of a gas turbine
US10794224B2 (en) * 2016-08-23 2020-10-06 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine and method of attaching a turbine nozzle guide vane segment of a gas turbine
US20190153883A1 (en) * 2017-11-21 2019-05-23 Doosan Heavy Industries & Construction Co., Ltd. First-stage turbine vane supporting structure and gas turbine including same
US11181003B2 (en) * 2017-11-21 2021-11-23 Doosan Heavy Industries & Construction Co., Ltd. First-stage turbine vane supporting structure and gas turbine including same

Also Published As

Publication number Publication date
JP2006097681A (ja) 2006-04-13
US20060062673A1 (en) 2006-03-23
JP4778758B2 (ja) 2011-09-21
CN1752416B (zh) 2011-10-05
DE102005045459A1 (de) 2006-04-06
DE102005045459B4 (de) 2016-06-09
CN1752416A (zh) 2006-03-29

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